Efficient Estimation of Effective Mass for Complex Structures under Base Excitations

Soucy, Y.; Etienne, Nicolas

doi:10.5589/q03-009

Cited by 9 publications

(7 citation statements)

References 1 publication

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“…Considering the base-motion excitation vectorz, according to structural dynamics basic theory [3], [14], the displacement vectorü is given by Eq. (11).…”

Section: Acceleration Response Of Mdof Systemsmentioning

confidence: 99%

An Easy-to-Implement Computational Method for the Spacecraft Sine Test-Prediction With Particular Emphasis on the Modal Contributions

Mucciante¹,

Caccamo²

2014

Proceedings of the 4th International Conference on Computational Methods in Structural Dynamics and Earthquake Engineering (COM

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“…Considering the base-motion excitation vectorz, according to structural dynamics basic theory [3], [14], the displacement vectorü is given by Eq. (11).…”

Section: Acceleration Response Of Mdof Systemsmentioning

confidence: 99%

An Easy-to-Implement Computational Method for the Spacecraft Sine Test-Prediction With Particular Emphasis on the Modal Contributions

Mucciante¹,

Caccamo²

2014

Proceedings of the 4th International Conference on Computational Methods in Structural Dynamics and Earthquake Engineering (COM

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“…In structural dynamics, the purpose of the effective modal mass is to select modes which have large reaction forces with respect to a rigid interface. When used during a base-driven analysis [4], the rigid interface is the base of a structure where the shaker acts and when used in the Craig-Bampton method [5], the interface is defined by the junction dofs connecting the studied substructure with the rest of the structure.…”

Section: Effective Modal Mass Indicatormentioning

confidence: 99%

Superelement Verification in Complex Structural Models

DuPont

Pillet

Cogan

2007

Shock and Vibration

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The objective of this article is to propose decision indicators to guide the analyst in the optimal definition of an ensemble of superelements in a complex structural assembly. These indicators are constructed based on comparisons between the unreduced physical model and the approximate solution provided by a nominally reduced superelement model. First, the low contribution substructure slave modes are filtered. Then, the minimum dynamical residual expansion is used to localize the superelements which are the most responsible for the response prediction errors. Moreover, it is shown that static residual vectors, which are a natural result of these calculations, can be included to represent the contribution of important truncated slave modes and consequently correct the deficient superelements. The proposed methodology is illustrated on a subassembly of an aeroengine model.

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“…The effective mass indicates the sensitivity of each mode to a base excitation (or spatial coupling between each mode and the excitation). 9,10 The frequency function H describes the sensitivity of each mode to the excitation frequency (or frequency coupling between the mode and the excitation). Obviously, each term of the summation of Eq.…”

Section: B Complex Tdofs: Simple Modelmentioning

confidence: 99%

Force-Limited Vibration Complex Two-Degree-of-Freedom System Method

Côté

Soucy

2004

AIAA Journal

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Force-limited vibration testing developed at the Jet Propulsion Laboratory offers many opportunities to decrease the overtesting problem associated with traditional vibration testing. Among the force-limited vibration methods, the complex two-degree-of-freedom system (TDOFS) appears to be the most complete and versatile model that gives reasonably conservative force limits and does not require extrapolation of interface force data for similar mounting structures and test articles. However, there are some limitations to the complex TDOFS model. The model is well adapted for nicely separated modes, but issues regarding the closely space modes have not been fully addressed in the literature. Also, the complex TDOFS model is based on free boundary conditions for the mounting structure, which appear to be natural for many cases such as spacecraft mounted on a launch vehicle. However, this is not necessarily true for some other cases such as an electronic component mounted on a spacecraft antenna, which requires fixed boundary conditions. Greater insights into the complex TDOFS method are given, and methodologies to overcome its limitations are proposed. It is shown that a simple approach can be used to assure conservative estimate of the force limits in situations regarding closely spaced modes. It is also demonstrated that, although the complex TDOFS method is not perfectly adapted to fixed boundary conditions of the mounting structure, given certain precautions, it still provides good estimates of the force limits.

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Efficient Estimation of Effective Mass for Complex Structures under Base Excitations

Cited by 9 publications

References 1 publication

An Easy-to-Implement Computational Method for the Spacecraft Sine Test-Prediction With Particular Emphasis on the Modal Contributions

An Easy-to-Implement Computational Method for the Spacecraft Sine Test-Prediction With Particular Emphasis on the Modal Contributions

Superelement Verification in Complex Structural Models

Force-Limited Vibration Complex Two-Degree-of-Freedom System Method

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